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<title> NACA 63(2)-215 (Velux Measurements) </title></head>

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<H1>NACA 63<font size="-1">(2)</font>-215 AIRFOIL</H1>
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Reynolds number = 1.1 x 10^6 <br><br>

Measured at Velux wind tunnel (see <A
HREF="./../HTML/biblio.htm#FuglsangASM">Fuglsang, Antoniou, S&oslash;rensen
and Madsen</A>) <br><br>

More details on computations and experimental facilities can be found in
the <A HREF="./../HTML/report.htm"><font color="#006699">Wind Turbine
Airfoil Catalogue</font></A>.


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<H1>DATA AVAILABLE:</H1><p><p>

- <A HREF="./prof.dat"> Airfoil shape </A><p>

<font size=+3> Experiments:<br> </font>
- <A HREF="./cldm.exp"> Lift, Drag and Moment Coefficients </A><p>

- <A HREF="./cp_05.741.exp"> Pressure Distribution - Angle of Attack = 05.741 deg. </A><br>
- <A HREF="./cp_10.238.exp"> Pressure Distribution - Angle of Attack = 10.238 deg. </A><br>
- <A HREF="./cp_12.112.exp"> Pressure Distribution - Angle of Attack = 12.112 deg. </A><br>
- <A HREF="./cp_15.578.exp"> Pressure Distribution - Angle of Attack = 15.578 deg. </A><br>
- <A HREF="./cp_17.347.exp"> Pressure Distribution - Angle of Attack = 17.347 deg. </A><br>
- <A HREF="./cp_19.393.exp"> Pressure Distribution - Angle of Attack = 19.393 deg. </A><p>

<font size=+3> XFOIL Computations:<br> </font>
- <A HREF="./cldm.xf"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./cfp_05.741.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 05.741 deg. </A><br>
- <A HREF="./cfp_10.238.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 10.238 deg. </A><br>
- <A HREF="./cfp_12.112.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 12.112 deg. </A><br>
- <A HREF="./cfp_15.578.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 15.578 deg. </A><br>
- <A HREF="./cfp_17.347.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 17.347 deg. </A><br>
- <A HREF="./cfp_19.393.xf"> Skin Friction and Pressure Distributions - Angle of Attack = 19.393 deg. </A><p>

<font size=+3> EllipSys2D Computations: </font><p>
<font size=+2><em>* Fully turbulent:</em><br> </font>
- <A HREF="./FULLYTURB/cldm.ellipsys"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./FULLYTURB/cp_05.741.ellipsys"> Pressure Distribution - Angle of Attack = 05.741 deg. </A><br>
- <A HREF="./FULLYTURB/cp_10.238.ellipsys"> Pressure Distribution - Angle of Attack = 10.238 deg. </A><br>
- <A HREF="./FULLYTURB/cp_12.112.ellipsys"> Pressure Distribution - Angle of Attack = 12.112 deg. </A><br>
- <A HREF="./FULLYTURB/cp_15.578.ellipsys"> Pressure Distribution - Angle of Attack = 15.578 deg. </A><br>
- <A HREF="./FULLYTURB/cp_17.347.ellipsys"> Pressure Distribution - Angle of Attack = 17.347 deg. </A><br>
- <A HREF="./FULLYTURB/cp_19.393.ellipsys"> Pressure Distribution - Angle of Attack = 19.393 deg. </A><p>

- <A HREF="./FULLYTURB/cf_05.741.ellipsys"> Skin Friction Distribution - Angle of Attack = 05.741 deg. </A> <br>
- <A HREF="./FULLYTURB/cf_10.238.ellipsys"> Skin Friction Distribution - Angle of Attack = 10.238 deg. </A> <br>
- <A HREF="./FULLYTURB/cf_12.112.ellipsys"> Skin Friction Distribution - Angle of Attack = 12.112 deg. </A> <br>
- <A HREF="./FULLYTURB/cf_15.578.ellipsys"> Skin Friction Distribution - Angle of Attack = 15.578 deg. </A> <br>
- <A HREF="./FULLYTURB/cf_17.347.ellipsys"> Skin Friction Distribution - Angle of Attack = 17.347 deg. </A> <br>
- <A HREF="./FULLYTURB/cf_19.393.ellipsys"> Skin Friction Distribution - Angle of Attack = 19.393 deg. </A> <p>

<font size=+2><em>* With transition model:</em><br> </font>
- <A HREF="./TRANSITION/cldm.ellipsys"> Lift, Drag and Moment Coefficients </A><p>
- <A HREF="./TRANSITION/cp_05.741.ellipsys"> Pressure Distribution - Angle of Attack = 05.741 deg. </A><br>
- <A HREF="./TRANSITION/cp_10.238.ellipsys"> Pressure Distribution - Angle of Attack = 10.238 deg. </A><br>
- <A HREF="./TRANSITION/cp_12.112.ellipsys"> Pressure Distribution - Angle of Attack = 12.112 deg. </A><br>
- <A HREF="./TRANSITION/cp_15.578.ellipsys"> Pressure Distribution - Angle of Attack = 15.578 deg. </A><br>
- <A HREF="./TRANSITION/cp_17.347.ellipsys"> Pressure Distribution - Angle of Attack = 17.347 deg. </A><br>
- <A HREF="./TRANSITION/cp_19.393.ellipsys"> Pressure Distribution - Angle of Attack = 19.393 deg. </A><p>

- <A HREF="./TRANSITION/cf_05.741.ellipsys"> Skin Friction Distribution - Angle of Attack = 05.741 deg. </A> <br>
- <A HREF="./TRANSITION/cf_10.238.ellipsys"> Skin Friction Distribution - Angle of Attack = 10.238 deg. </A> <br>
- <A HREF="./TRANSITION/cf_12.112.ellipsys"> Skin Friction Distribution - Angle of Attack = 12.112 deg. </A> <br>
- <A HREF="./TRANSITION/cf_15.578.ellipsys"> Skin Friction Distribution - Angle of Attack = 15.578 deg. </A> <br>
- <A HREF="./TRANSITION/cf_17.347.ellipsys"> Skin Friction Distribution - Angle of Attack = 17.347 deg. </A> <br>
- <A HREF="./TRANSITION/cf_19.393.ellipsys"> Skin Friction Distribution - Angle of Attack = 19.393 deg. </A>


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<H1>FIGURES AVAILABLE: (PostScript files)</H1><p><p>

- <A HREF="./../NACA-WS/NACA-63-215/PS/profile.ps"> Airfoil shape </A><p>

- <A HREF="./PS/cl.ps"> Lift Coefficient </A><br>
- <A HREF="./PS/cd.ps"> Drag Coefficient </A><br>
- <A HREF="./PS/cm.ps"> Moment Coefficient </A><p>

- <A HREF="./PS/cp_a05.741.ps"> Pressure Distribution - Angle of Attack = 05.741 deg. </A><br>
- <A HREF="./PS/cp_a10.238.ps"> Pressure Distribution - Angle of Attack = 10.238 deg. </A><br>
- <A HREF="./PS/cp_a12.112.ps"> Pressure Distribution - Angle of Attack = 12.112 deg. </A><br>
- <A HREF="./PS/cp_a15.578.ps"> Pressure Distribution - Angle of Attack = 15.578 deg. </A><br>
- <A HREF="./PS/cp_a17.347.ps"> Pressure Distribution - Angle of Attack = 17.347 deg. </A><br>
- <A HREF="./PS/cp_a19.393.ps"> Pressure Distribution - Angle of Attack = 19.393 deg. </A><p>

- <A HREF="./PS/cf_a05.741.ps"> Skin Friction Distribution - Angle of Attack = 05.741 deg. </A><br>
- <A HREF="./PS/cf_a10.238.ps"> Skin Friction Distribution - Angle of Attack = 10.238 deg. </A><br>
- <A HREF="./PS/cf_a12.112.ps"> Skin Friction Distribution - Angle of Attack = 12.112 deg. </A><br>
- <A HREF="./PS/cf_a15.578.ps"> Skin Friction Distribution - Angle of Attack = 15.578 deg. </A><br>
- <A HREF="./PS/cf_a17.347.ps"> Skin Friction Distribution - Angle of Attack = 17.347 deg. </A><br>
- <A HREF="./PS/cf_a19.393.ps"> Skin Friction Distribution - Angle of Attack = 19.393 deg. </A><p>



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